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| Overview | | Description | | USNEWPAN | | Aeroelastics | | 3D Optimisation | | Free Surface | | For Existing Panel Method Users |

NEWPAN-MSC.Nastran™ Aeroelastics

In recent years Flow Solutions has focussed considerable effort in the area of static and dynamic aeroelasticity, working in close collaboration with MSC.Software to provide coupled aero-structural solutions.

Static Aeroleasticity

  • Non-linear analysis of the aero-structural coupled problem
  • "Free flight" aerodynamic loads, with stuctural deformation
  • Splining procedure between aero and structural mesh
  • Iterative analysis with rapid convergence
  • Full NEWPAN aerodynamics- true wetted surface of complex configurations
More information on the coupled static aeroelastic process is available here.

Trim Solver

  • Fully automated capability for controller trim for level flight
  • Iterative NEWPAN-MSC.Nastran™ coupling
  • An enhanced capability with direct communication to the MSC.Nastran™ database is planned

Dynamic Aeroelasticity

  • Directly coupled USNEWPAN-MSC.Nastran™ flutter analysis
  • Dynamic solutions about the fully trimmed, static aeroelastically deformed, configuration
  • Full NEWPAN aerodynamics- true wetted surface, i.e. including all incidence and thickness effects, for complex configurations
  • Direct communication of NEWPAN/USNEWPAN aerodynamics to the MSC.Nastran™ database
  • Maneuver simulations, eg pull up
  • Gust analysis (in progress)
  • Aerodynamic solutions for any combination of incidence, (subsonic) Mach number, and reduced frequency parameter
  • A fast and practical capability with much higher fidelity aerodynamics than DLM
More information on USNEWPAN based flutter analysis is available here.


As an example of the powerful capability provided by coupled NEWPAN-MSC.Nastran™, Flow Solutions and MSC.Software have prepared an aeroelastic analysis of a complete light airplane. This includes full, detailed modelling of the structure, including all controllers (rudder, elevators, ailerons) and complete wetted area modelling of all aerodynamic surfaces. Such a model allows a detailed investigation of both static and dynamic aeroelastic effects, including checks for flutter.

Presented here are the results, at a 200km/h, 1g point in the flight envelope, for the structural mode determined to be critical - namely fuselage bending/torsion. The instantaneous surface pressure coefficients (i.e. steady mean plus unsteady perturbation), are shown along with the accompanying structural deflections and aerodynamic force vectors.

The unsteady analysis was performed after a full static aeroelastic analysis to establish the trimmed and deformed mean configuration at the specific point in the flight envelope. Using this starting point, USNEWPAN was run in MSC.Nastran™ coupled mode. This provides the results for the steady flow, plus the unsteady aerodynamic perturbations, in the frequency domain, in matrix form, for the requested Mach numbers and reduced frequency parameters. The aerodynamic results are communicated directly into the MSC.Nastran™ database. This enables the complete range of flutter postprocessing tools to be used, for instance.

The aerodynamic model was created in the GEMS preprocessor as a 5839 panel full model. NEWPAN/USNEWPAN is a fast and practical tool, able to populate the aeroelastic database with dozens, or hundreds, of aerodynamic datasets in a realistic timescale. For this complete model, here is an example of the runtime:

Pentium P4 3.2GHz single CPU desktop PC 5839 panels full light aircraft Incompressible, steady, 5 wake relaxations, PLUS unsteady frequency domain, 1 reduced frequency, 6 modes: 5.1 minutes



MSC.Nastran,MSC.Patran and MSC.Flightloads are trademarks of MSC.Software Corporation.


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